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NACA M14 AIRFOIL (m14-il)

NACA M14 AIRFOIL - NACA/Munk M-14 airfoil


Airfoil m14-il
Details Dat file Parser  
(m14-il) NACA M14 AIRFOIL
NACA/Munk M-14 airfoil
Max thickness 8.1% at 30% chord.
Max camber 3.9% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M14 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0153100
 0.0250000 0.0230300
 0.0500000 0.0346500
 0.0750000 0.0441800
 0.1000000 0.0518000
 0.1500000 0.0636500
 0.2000000 0.0721000
 0.3000000 0.0800000
 0.4000000 0.0797000
 0.5000000 0.0732000
 0.6000000 0.0625000
 0.7000000 0.0491000
 0.8000000 0.0346000
 0.9000000 0.0195000
 0.9500000 0.0119500
 1.0000000 0.0042000

 0.0000000 0.0000000
 0.0125000 -.0110900
 0.0250000 -.0120700
 0.0500000 -.0119500
 0.0750000 -.0108200
 0.1000000 -.0094000
 0.1500000 -.0063500
 0.2000000 -.0036000
 0.3000000 -.0006000
 0.4000000 -.0009000
 0.5000000 -.0025000
 0.6000000 -.0044000
 0.7000000 -.0059000
 0.8000000 -.0055000
 0.9000000 -.0042000
 0.9500000 -.0024500
 1.0000000 0.0000000
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Lednicer format dat file
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Polars for NACA M14 AIRFOIL (m14-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m14-il50,000938.1 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   m14-il50,000538.8 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m14-il100,000957.3 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m14-il100,000557.4 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m14-il200,000976.8 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m14-il200,000575.4 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   m14-il500,0009102.9 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m14-il500,000598.1 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m14-il1,000,0009121.9 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m14-il1,000,0005113.7 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
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